Aircraft mission computing system, comprising a computing engine for computing an aircraft trajectory during the mission and related process

1. An aircraft mission computing system, comprising a computing engine configured to compute an aircraft trajectory for a mission, the computing engine comprising a memory and a processor configured to control the aircraft mission computing system via instructions from the memory to: initialize mission specifications of a mission, the mission specifications including at least a geographical point of origin, a geographical destination point, and operational mission specifications; recover a weather context in an airspace between the geographical point of origin and the geographical destination point; determine airplane performance based on the operational mission specifications and based on the weather context; compute a mission trajectory between the geographical point of origin and the geographical destination point as a function of the airplane performance and as a function of the operational mission specifications; and compute at least one isochronous curve or fuel iso-consumption curve of the aircraft from at least one point of the mission trajectory and being configured to determine at least one other point of the mission trajectory on the at least one isochronous curve or fuel iso-consumption curve of the aircraft, the isochronous curve being a curve connecting possible alternative points accessible to the aircraft in the future from a given point at a given time in a time increment, the possible alternative points on the isochronous curve only capable of being part of the mission trajectory independent of each other, the fuel iso-consumption curve being a curve connecting possible alternative points accessible to the aircraft from the given point with a given fuel consumption in a consumed fuel increment, the possible alternative points on the fuel iso-consumption curve only capable of being part of the mission trajectory independent of each other.

2. The system according to claim 1 , wherein each point of the mission trajectory is located on the at least one isochronous curve or fuel iso-consumption curve relative to another point of the mission trajectory.

3. The system according to claim 2 , wherein the computing engine is configured to determine the at least one other point of the mission trajectory on the at least one isochronous curve or fuel iso-consumption curve as a function of operational or performance airplane specifications.

4. The system according to claim 1 , wherein the computing engine is configured to compute a plurality of isochronous curves or fuel iso-consumption curves on a plurality flight levels from the at least one point of the mission trajectory.

5. The system according to claim 4 , wherein the computing engine is configured to determine the plurality of isochronous curves or fuel iso-consumption curves on the plurality of flight levels from an initial point to a first flight level change curve and to define at least a first trajectory segment for each flight level between the initial point and the first flight level change curve, the computing engine being configured to subsequently determine the plurality of iso-movement curves from the first flight level change curve for the plurality of flight levels to a second flight level change curve and to define at least a second trajectory segment for each of the plurality of flight levels between the first flight level change curve and the second flight level change curve, the computing engine being configured to subsequently define at least one trajectory by combining successive trajectory segments chosen from among the first and second trajectory segments defined for each plurality of flight levels.

6. The system according to claim 1 , wherein the computing engine is configured to compute a center of gravity of the aircraft and to compute at least an aircraft performance en-route as a function of the computed center of gravity, and as a function of the operational mission specifications of the aircraft, the computing engine being configured to compute at least one mission parameter based on the mission trajectory by using the aircraft performance en-route.

7. The system according to claim 6 , wherein the at least one mission parameter is a weight at takeoff or a weight at landing of the aircraft adapted for the aircraft to carry out the mission trajectory or the at least one mission parameter is a total distance traveled by the aircraft over the mission trajectory.

8. The system according to claim 6 , wherein the at least one mission parameter is a weight at takeoff or a weight at landing of the aircraft on a given terrain, the computing engine configured to determine a maximum weight of the aircraft allowing the aircraft to take off or land on the given terrain, the computing unit being configured to verify that the weight at takeoff or the weight at landing of the aircraft obtained using the aircraft perfomance en-route is less than or equal to the determined maximum weight allowing the aircraft to take off or land on the given terrain obtained using the computing engine.

9. The system according to claim 1 , wherein the computing engine is configured to compute a first given trajectory, the computing engine being configured to determine, based on the first given trajectory, at least one mission parameter of the aircraft, the computing engine being configured to subsequently compute at least one other given trajectory of the aircraft, until the at least one mission parameter converges toward a desired mission parameter value.

10. The system according to claim 1 , wherein at least one of the operational mission specifications includes an airplane context or includes a mission context, the computing engine being configured to determine the airplane performance as a function of the airplane context or of the mission context.

11. The system according to claim 10 , wherein the airplane context is a type of defective equipment, a dispatch or a failure.

12. The system according to claim 10 , wherein the mission context is an imposed airway, a prohibited zone or a desired passage zone.

13. An aircraft mission trajectory computing method, comprising: acquiring specifications of a mission including at least a geographical point of origin, a geographical destination point, and operational mission specifications; recovering a weather context in the airspace between the geographical point of origin and the geographical destination point; determining airplane performance, as a function of operational mission specifications and of the weather context; computing at least one mission trajectory between the geographical point of origin and the geographical destination point as a function of the airplane performance and operational mission specifications, the computing of the at least one mission trajectory comprising computing at least one isochronous curve or fuel iso-consumption curve of the aircraft from at least one point of the at least one mission trajectory, and determining at least one other point of the at least one airplane trajectory on the at least one isochronous curve or fuel iso-consumption curve, the isochronous curve being a curve connecting possible alternative points accessible to the aircraft in the future from a given point at a given time in a time increment, the possible alternative points on the isochronous curve only capable of being part of the mission trajectory independent of each other, the fuel iso-consumption curve being a curve connecting possible alternative points accessible to the aircraft from the given point with a given fuel consumption in a consumed fuel increment, the possible alternative points on the fuel iso-consumption curve only capable of being part of the mission trajectory independent of each other.

14. The method according to claim 13 , wherein each point of the at least one mission trajectory is located on the at least one isochronous curve or fuel iso-consumption curve relative to another point of the at least one mission trajectory.

15. The method according to claim 13 wherein the determining of the at least one other point of the at least one airplane trajectory on the at least one isochronous curve or fuel iso-consumption curve is a function of the operational mission specifications and/or performance airplane specifications.

16. The method according to claim 13 wherein the computing of the at least one isochronous curve or fuel iso-consumption curve of the aircraft comprises computing a plurality of isochronous curves or fuel iso-consumption curves on several flight levels from the point of the at least one mission trajectory.

17. The method according to claim 16 the computing of the at least one mission trajectory comprises: computing an aircraft weight and balance to compute a center of gravity of the aircraft, computing a performance en-route of the aircraft as a function of the computed center of gravity, and as a function of the operational mission specifications of the aircraft, and computing a mission parameter based on the at least one mission trajectory by using the performance en-route computation.

18. The method according to claim 13 wherein the computing of the at least one mission trajectory comprises: computing a first given trajectory, and determining, based on the first given trajectory, a value of at least one mission parameter of the aircraft, then computing at least one other given trajectory of the aircraft and one other value of the at least one mission parameter of the aircraft, until a convergence criterion on the value of the at least one mission parameter of the aircraft is reached.